A nosecone apparatus for hypersonic aircraft, rocket or missiles using a method for the mitigation of the created the shock front of a rocket or aerospace plane flying at hypersonic speeds by using nosecone splines to create both centripetal and isentropic airflows in conjunction with regeneratively cooling the nosecone structure.
System, apparatus and methods for a nosecone and a propulsive nozzle
2020-09-22
Patent
Electronic Resource
English
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